CN104132795A - Model rope supporting system capable of realizing wind tunnel virtual flight - Google Patents
Model rope supporting system capable of realizing wind tunnel virtual flight Download PDFInfo
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- CN104132795A CN104132795A CN201410392466.0A CN201410392466A CN104132795A CN 104132795 A CN104132795 A CN 104132795A CN 201410392466 A CN201410392466 A CN 201410392466A CN 104132795 A CN104132795 A CN 104132795A
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Abstract
The invention relates to air vehicle models, in particular to a model rope supporting system capable of realizing wind tunnel virtual flight. The model rope supporting system is provided with an airplane model, a rod type six-component balance, a front taper sleeve, a rear taper sleeve, a sleeve and a supporting rod. The airplane model is pulled and hung by a pulling rope, one end of the pulling rope is connected to a winch motor assembly through a pulley, and the other end of the pulling rope is connected with the connecting rod and used for hanging and supporting the airplane model; the rod type six-component balance is coaxially arranged in the airplane model, the front end of the rod type six-component balance is connected with the front taper sleeve through bolts, and the rear end of the rod type six-component balance is connected with the rear taper sleeve through bolts; the sleeve is fixedly connected to the rear taper sleeve through bolts and installed parallel to the rod type six-component balance without making contact with the surface of the rod type six-component balance; the airplane model is locked to the front taper sleeve through bolts, the supporting rod is arranged on the sleeve and used for tying the pulling rope, and the pulling rope is connected with a pulley arranged on an external base. The model rope supporting system is easy and convenient to install and high in generality, the influence on a flow field is small, and testing is convenient.
Description
Technical field
The present invention relates to dummy vehicle, especially relate to a kind of model rope support system that realizes wind-tunnel virtual flight with built-in six component balance.
Background technology
Wind tunnel test is prediction aircraft aeroperformance, obtains one of topmost means of the required key aerodynamic parameter of Flight Vehicle Design.Wind tunnel test is also to carry out one of Main Means of aerodynamics fundamental research and applied research, thereby has extremely important effect.
In wind tunnel test, generally obtain required various aerodynamic loading data by six component balance.Wherein rod-type six component balance, because simple in structure, measuring accuracy is high and be widely used in aerodynamic parameter measure.Traditional way is that rod type six component balance, is installed in series in support bar, and model aircraft is arranged on six component balance, end again, i.e. the rigid supporting way of most widely used series connection.But the rigid supporting way of connecting brings unavoidable test error, this is mainly because the rigid support of series connection has changed original design external form of model aircraft, makes near the mobile off-design state of model supporting; When for dynamic test, also make the zone of action, amplitude and the frequency of non-Unsteady Flow change, thereby the distortion that causes dynamic derivative to measure.Support bar vibration is that another causes aerodynamic derivative to measure the key factor of distortion.
Chinese patent CN 30910070056.3 discloses a kind of two-degree freedom rope traction and parallel-connection mechanism, this mechanism comprises frame and moving platform, it is characterized in that this mechanism also comprises a middle pole and two groups of cable traction side chains, described middle pole is made up of two orthogonal cradle head hinges, and is arranged on the center between frame and moving platform; Described two groups of cable traction branched structures are identical, and centered by middle pole, cross side chain and the moving platform center of being arranged on; Each group cable traction side chain drives by the motor being fixed in frame, and driven by motor rope drives moving platform to rotate around described middle pole through tensioning system and pulley mechanism, realizes moving platform and rotates in two orthogonal directions.This invention has just realized the rope traction control campaign of moving platform two degree-of-freedom motion, relatively simple for structure.The moving platform of this mechanism is not model aircraft, does not consider that the aerodynamic parameter of model is measured yet, and can not be used for wind tunnel test.
The open a kind of rope traction wall of Chinese patent CN 31210086974.7 promotes carrying parallel institution, has designed a kind of for building the carrying mechanism of industrial and commercial bank's industry and wall upkeep operation.This invention drives four groups of traction ropes with four groups of motors, drives weight to rise along wall; Mechanism's work space is large, support stiffness is high, the power consumption of stable work in work, mechanism is low.The model that this invention cannot be served as wind tunnel test equally supports.
Chinese patent CN 31210552298.8 discloses a kind of traction of the change structure rope for wind tunnel test parallel robot.Be provided with frame, model aircraft, traction rope, movable universal hinge; Model aircraft is restricted to draw realizes six-freedom motion; Movable hinge driven unit is provided with movable hinge bearing, ball-screw, guide rail, bearing, motor, shaft coupling; Traction rope driven unit is provided with rope traction bearing, ball screw, guide rail, screw mandrel bearing spider, motor, shaft coupling; Fixing universal hinge and movable universal hinge are respectively equipped with zanjon slit roller, universal bearing, axle, set nut, vertical bearing and horizontal seat.The advantage of this invention be to air flow field disturb little, pilot project is diversified, work space is large, fast response time, overcomes traditional rigid wind-tunnel supporting way and destroys air flow field, experimental project is single, model sport space is little, response speed is slow shortcoming; Simple in structure, be easy to manufacture and safeguard.This invention can realize the Static and dynamic test in wind-tunnel of rope traction and parallel-connection mechanism, blemish in an otherwise perfect thing, and this invention does not propose measurement and the calculation method of aerodynamic loading, has ignored the most key problem of wind tunnel test.
Summary of the invention
The object of the invention is to solve the measurement problem of cable traction parallel institution model aerodynamic parameter in the time being applied to wind tunnel test, provide simple in structure, easy for installation, highly versatile, stream field to disturb little, can be applied in various wind tunnel tests, be built-in with a kind of model rope support system that realizes wind-tunnel virtual flight of six component balance.
The present invention is provided with model aircraft, rod-type six component balance, front tapered sleeve, rear tapered sleeve, sleeve and pole, model aircraft is hung by traction rope traction, one end of traction rope is connected to winch motor assembly by pulley, the other end of traction rope is connected with pole, for hanging and support model aircraft, rod-type six component balance, is located in model aircraft, rod-type six component balance, is coaxial with model aircraft, the front end of rod-type six component balance, is by being connected with front tapered sleeve, the rear end of rod-type six component balance, is connected with rear tapered sleeve by bolt, sleeve is fixed on rear tapered sleeve by bolt, sleeve installation parallel with rod-type six component balance, but contactless with rod-type six component balance, surface, model aircraft puts at inner cone by locked with bolts, pole is located on sleeve, being used for is traction rope, traction rope is connected with the pulley of being located at outside pedestal.
The present invention is connected in rear tapered sleeve by sleeve by fastening bolt, and rear tapered sleeve is connected with the rear end of rod-type six component balance,, and sleeve is provided with some short struts.Short strut, through model of an airplane wall preformed hole, is connected with drag rope, thereby has completed the fixing of rod-type six component balance; On the other hand, model aircraft is connected with the front end of rod-type six component balance, by front tapered sleeve, but contactless with sleeve and short strut.In wind tunnel test, the aerodynamic force and the aerodynamic moment that are carried on model aircraft are delivered to rod-type six component balance,, cause that rod-type six component balance, foil gauge produces deformation; Foil gauge deformation converts electrical signal transfer to computer acquisition storage, thereby completes the measurement of aerodynamic parameter; By controlling, change the length of drag rope, can adjust the pose of model aircraft, make it complete six-freedom motion, to meet the requirement of wind tunnel test to model sport state.
The present invention, to being originally applied to the rod-type six component balance, of wind-tunnel series connection support system, through ingehious design, has been applied in wire-driven parallel support system, thereby has solved the measurement problem of wire-driven parallel support system aerodynamic parameter in wind tunnel test.This kind of mode simple installation, little to Flow Field in Wind Tunnel interference, can greatly improve the measuring accuracy of rope traction and parallel-connection mechanism in wind tunnel test, has improved the usable value of this type of results of wind tunnel.The progress of the novel rope traction and parallel-connection mechanism support system that the present invention proposes in wind-tunnel static state and dynamic test has great importance.
Tool of the present invention has the following advantages:
1. simple installation.The present invention adopts model and the mode that rod-type six component balance,, rod-type six component balance, are connected with sleeve and drag rope, can realize easily the installation of rod-type six component balance, in model aircraft.
2. highly versatile.For the various rod-type six component balance,s of different model, only need be equipped with corresponding sleeve, can be built in model, embed in wire-driven parallel support system, do not affect the original measuring accuracy of rod-type six component balance, and calibrating mode.
3. stream field impact is little.Than traditional supporting way, farthest eliminate because the existence of supporting mechanism changes the original design outline of model to aerodynamic parameter measurement and caused the harmful effect of error.
4. test is convenient.According to testing requirements, programme by computing machine, can control Fei Ji ?balance integration model carry out rotation and the translation motions such as pitching, driftage, rolling, realize wind-tunnel virtual flight, complete easily static state, the various test missions such as dynamic.
Brief description of the drawings
Fig. 1 is the embodiment of the present invention 1 installation diagram.
Fig. 2 is the embodiment of the present invention 1 sectional view.
Fig. 3 is the critical component balance component detail figure of Fig. 2.
Fig. 4 is the embodiment of the present invention 2 installations diagram.
Fig. 5 is the embodiment of the present invention 2 sectional views.
Fig. 6 is the detail view of the critical component balance assembly in Fig. 5.
Embodiment
Following examples will be illustrated two kinds of specific designs of the present invention and mounting means.
Embodiment 1
The embodiment of the present invention is provided with model aircraft 1, rod-type six component balance, 6, front tapered sleeve 7, rear tapered sleeve 14, sleeve 12 and pole 5, model aircraft 1 draws suspension by traction rope 2, one end of traction rope 2 is connected to winch motor assembly 4 by pulley 3, the other end of traction rope 2 is connected with pole 5, for hanging and support model aircraft 1, rod-type six component balance, 6 is located in model aircraft 1, rod-type six component balance, 6 is coaxial with model aircraft 1, the front end of rod-type six component balance, 6 is connected with front tapered sleeve 7 by 8, the rear end of rod-type six component balance, 6 is connected with rear tapered sleeve 14 by bolt 15, sleeve 12 is fixed on rear tapered sleeve 14 by bolt 17, sleeve 12 installation parallel with rod-type six component balance, 6, but contactless with rod-type six component balance, 6 surfaces, model aircraft 1 is locked on front tapered sleeve 7 by bolt 10, pole 5 is located on sleeve 12, being used for is traction rope 2, traction rope 2 is connected with the pulley 3 of being located at outside pedestal.
Fig. 1 is the schematic diagram of the embodiment of the present invention 1.Fig. 2 is the sectional view of embodiment 1, has provided the details of relation between built-in rod-type six component balance, and model.
In Fig. 1, for making model complete six-freedom motion, at least need seven drag ropes.Model aircraft 1 is hung up by some traction rope 2 tractions.Traction rope 2 one end are connected to winch motor assembly 4 (being reduced to cube piece in Fig. 1, Fig. 4) by pulley 3, and the other end is connected with model aircraft assembly pole 5, work to hang and support model aircraft.For drawing for purpose of brevity, part rope omitted and does not draw with being connected of pulley.Change the length of traction rope 2, can adjust the pose of model aircraft, to meet the requirement of wind tunnel test.
In conjunction with Fig. 2 and Fig. 3, can understand easily design of the present invention.Fig. 2 is the longitudinal sectional drawing of model fuselage and rod-type six component balance, in the embodiment of the present invention 1.Fig. 3 is the detail view of rod-type six component balance, assembly in embodiment 1.Rod-type six component balance, 6 is placed in model aircraft 1, and both are coaxial.What be connected with rod-type six component balance, 6 is front tapered sleeve 7 and rear tapered sleeve 14.Bolt 8 is connected front tapered sleeve 7 and the front end of rod-type six component balance, 6, and bolt 15 is connected rear tapered sleeve 14 with rod-type six component balance, 6 rear ends.Sleeve 12 is fixed on rear tapered sleeve 14 by bolt 17, and installation parallel with rod-type six component balance, 6 is contactless with rod-type six component balance, 6 surfaces, also contactless with model aircraft fuselage.Bolt 10 is locked in fuselage on front tapered sleeve 7.Head 11 inserts fuselage, by screw 9, head 11 and fuselage is fixed.Sleeve 12 is provided with some poles 5, for being traction rope.On fuselage, reserve the diameter hole 13 larger than pole for making pole 5 stretch out fuselage.The length of pole and the method for tether all will be to reduce interference in air flow as degree as far as possible, and must ensure that pole 5 and institute's tether are all contactless state with model all the time.Cavity in model tail plug 16 can be placed the inertia system of measurement model attitude.For ease of installing, model above the waist (back) has designed the aircraft back lid 18 that can raise.
Traction rope 2 is connected on the pulley 3 of outside pedestal, thereby completes the fixing of rod-type six component balance, assembly.In the time that motor drives winch work, can change the length of traction rope.Under the traction of rope system, model can complete the various motions such as pitching, driftage, vibration.
The suffered aerodynamic force of model aircraft and aerodynamic moment are delivered to rod-type six component balance, front end by balance front end tapered sleeve 7, cause the deformation of rod-type six component balance, foil gauge, convert the effect of aerodynamic force to electrical quantity signal, then machine collection storage as calculated, thereby complete the collection of data.In whole process of the test, between model aircraft 1 and sleeve 12, do not contact, pole 5 does not also contact with aircraft with traction rope 2, with the independence that ensures that rod-type six component balance, is measured.
Model head 11, tail sealing plug 16 and model of an airplane back lid 18 have been designed to removably, facilitate model aircraft intraware to install and trouble hunting.
Embodiment 2
Fig. 4 is the schematic diagram of the embodiment of the present invention 2.The installation fixed form of model aircraft and rod-type six component balance, assembly is with embodiment 1.In conjunction with the embodiment sectional view of Fig. 5 and the balance component detail figure of Fig. 6, known, embodiment 2 with the difference of embodiment 1 is, there is no tail plug, be located at the extended prolongation hollow tubular 19 that stretches out tail of the rear tapered sleeve 14 of balance rear end, on prolongation hollow tubular 19, be provided with some ramuscule bars 5, for being traction rope.
Embodiment 2 is the application extensions to embodiment 1.Can require to adopt different embodiment with test objective according to the aerodynamic arrangement of model external form, or the plug 16 of employing embodiment 1, or adopt being added with in embodiment 2 to extend hollow tubular 19, change the layout of rope system, thereby change the node configuration of rope traction and parallel-connection mechanism, play the effect of supporting and controlling model aircraft pose.
Built-in bar-type six component balance, in model aircraft, drag rope is in order to bolster model and six component balance,, and driving model carries out the 6DOF motion of virtual flight.
Each drag rope is connected with the assembly such as winch, motor by pulley or pulley system, drive winch to drive drag rope move and adjust rope lengths by computer control motor, carry out the motion of 6DOF thereby control model aircraft, change position and the attitude of model.Rod-type six component balance, is provided with parallel sleeve cylinder outward, and is provided with forward and backward connection tapered sleeve.Described sleeve is connected tapered sleeve with balance rear end can be processed respectively, also can be used as a subassembly; Described model aircraft is connected tapered sleeve with balance front end can be processed respectively, also can be used as a subassembly.Head, tail and back are designed to can resolution model, facilitates installation and the trouble hunting of model and balance.
Claims (1)
1. can realize the model rope support system of wind-tunnel virtual flight for one kind, it is characterized in that being provided with model aircraft, rod-type six component balance, front tapered sleeve, rear tapered sleeve, sleeve and pole, model aircraft is hung by traction rope traction, one end of traction rope is connected to winch motor assembly by pulley, the other end of traction rope is connected with pole, for hanging and support model aircraft, rod-type six component balance, is located in model aircraft, rod-type six component balance, is coaxial with model aircraft, the front end of rod-type six component balance, is by being connected with front tapered sleeve, the rear end of rod-type six component balance, is connected with rear tapered sleeve by bolt, sleeve is fixed on rear tapered sleeve by bolt, sleeve installation parallel with rod-type six component balance, but contactless with rod-type six component balance, surface, model aircraft puts at inner cone by locked with bolts, pole is located on sleeve, being used for is traction rope, traction rope is connected with the pulley of being located at outside pedestal.
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| CN201410392466.0A CN104132795B (en) | 2014-08-11 | 2014-08-11 | A kind of model cable support system realizing wind-tunnel virtual flight |
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| CN201410392466.0A CN104132795B (en) | 2014-08-11 | 2014-08-11 | A kind of model cable support system realizing wind-tunnel virtual flight |
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| CN104132795A true CN104132795A (en) | 2014-11-05 |
| CN104132795B CN104132795B (en) | 2016-06-15 |
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| CN105300595A (en) * | 2015-11-27 | 2016-02-03 | 中国航空工业集团公司沈阳空气动力研究所 | Balance loading head with calibration of connected model and loading method |
| CN106017797A (en) * | 2016-05-12 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | Unmanned aerial vehicle inertia measuring device and unmanned aerial vehicle inertia measuring method |
| CN106680792A (en) * | 2017-01-13 | 2017-05-17 | 厦门大学 | Horizontal type low-scattering object suspension system used for electromagnetic scattering measurement |
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| CN107860550A (en) * | 2017-10-23 | 2018-03-30 | 中国科学院力学研究所 | A kind of method for supporting for being used for dummy vehicle in wind tunnel experiment |
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| CN108844707A (en) * | 2018-09-04 | 2018-11-20 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind-tunnel routine test model support sting vibration absorber |
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| CN114778064A (en) * | 2022-04-19 | 2022-07-22 | 厦门大学 | Supporting device and test system for wind tunnel virtual flight test of rotary aircraft model |
| CN114838905A (en) * | 2022-03-23 | 2022-08-02 | 厦门大学 | Novel method for measuring dynamic aerodynamic force of rope-series parallel support aircraft model |
| CN115655635A (en) * | 2022-12-14 | 2023-01-31 | 中国空气动力研究与发展中心高速空气动力研究所 | Two-freedom-degree supporting system for full-body freedom-degree flutter or gust test |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU609072A1 (en) * | 1976-08-17 | 1978-05-30 | Предприятие П/Я Р-6397 | Stand for aerodynamic testing of air-cushion vehicle model |
| US5627311A (en) * | 1994-08-23 | 1997-05-06 | National Aerospace Laboratory Of Science & Technology Agency | Transportable three-dimensional calibration wind tunnel system, verification method of flight control system and flight simulator using same |
| CN101793591A (en) * | 2010-03-26 | 2010-08-04 | 北京航空航天大学 | Aircraft aero-servo-elasticity ground simulating test system |
| KR20120033850A (en) * | 2010-09-30 | 2012-04-09 | 건국대학교 산학협력단 | Driving force measurement installation of flapping-wing system and the method |
| CN202420817U (en) * | 2012-01-18 | 2012-09-05 | 汪选要 | Parallel flexible cable traction mechanism applied to wind tunnel test on aircraft |
| CN102798510A (en) * | 2012-09-12 | 2012-11-28 | 吉林大学 | Supporting device for automotive wind tunnel experiment model |
| CN103009391A (en) * | 2012-12-14 | 2013-04-03 | 厦门大学 | Variable-structure rope-traction parallel robot for wind tunnel test |
-
2014
- 2014-08-11 CN CN201410392466.0A patent/CN104132795B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU609072A1 (en) * | 1976-08-17 | 1978-05-30 | Предприятие П/Я Р-6397 | Stand for aerodynamic testing of air-cushion vehicle model |
| US5627311A (en) * | 1994-08-23 | 1997-05-06 | National Aerospace Laboratory Of Science & Technology Agency | Transportable three-dimensional calibration wind tunnel system, verification method of flight control system and flight simulator using same |
| CN101793591A (en) * | 2010-03-26 | 2010-08-04 | 北京航空航天大学 | Aircraft aero-servo-elasticity ground simulating test system |
| KR20120033850A (en) * | 2010-09-30 | 2012-04-09 | 건국대학교 산학협력단 | Driving force measurement installation of flapping-wing system and the method |
| CN202420817U (en) * | 2012-01-18 | 2012-09-05 | 汪选要 | Parallel flexible cable traction mechanism applied to wind tunnel test on aircraft |
| CN102798510A (en) * | 2012-09-12 | 2012-11-28 | 吉林大学 | Supporting device for automotive wind tunnel experiment model |
| CN103009391A (en) * | 2012-12-14 | 2013-04-03 | 厦门大学 | Variable-structure rope-traction parallel robot for wind tunnel test |
Non-Patent Citations (1)
| Title |
|---|
| 姚裕等: "《新型风洞测力实验一体化装备研究展望》", 《第一届近代实验空气动力学会议论文集》 * |
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| Publication number | Publication date |
|---|---|
| CN104132795B (en) | 2016-06-15 |
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